Author: Lyndell S. King

Publisher:

Published: 1973

Total Pages: 132

ISBN-13:

Wind tunnel tests were conducted to determine the flow distribution about fuselage configurations at transonic and supersonic speeds and at angles of attack up to 20 degrees. The models tested were approximately one-twelfth scale and consisted of a main fuselage forebody member and several attachable components. The components were mounted in several combinations to represent different possible configurations for tactical aircraft. Flow distribution surveys were conducted at two inlet locations ahead of and under the wing to assess the effects of forebody geometry for the conditions indicated. The data indicate the influence of the canopy, nose droop, and fuselage shape on flow angularities in the forward survey plane.